Internal core profile for a turbine nozzle airfoil

ABSTRACT

An airfoil profile for a second stage turbine nozzle of a gas turbine is provided. The turbine nozzle may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.

TECHNICAL FIELD

This application relates to airfoils for a gas turbine and moreparticularly to an airfoil profile for a second stage turbine nozzle ofa gas turbine that has a variable thickness and three-dimensional (“3D”)shape along the airfoil span to improve airfoil mean stress and dynamicstress capabilities of the turbine nozzle.

BACKGROUND

Turbines are machines that obtain rotational force by impulsive orreaction force using a flow of a compressible fluid such as steam orgas, and include a steam turbine using steam, a gas turbine using hotcombustion gas, and so on.

The gas turbine includes a compressor, a combustor, and a turbine. Thecompressor includes an air inlet into which air is introduced, and aplurality of compressor vanes and a plurality of compressor blades whichare alternately arranged in a compressor housing. The introduced air iscompressed by the compressor vanes and the compressor blades whilepassing through an inside of the compressor.

The combustor mixes fuel with compressed air supplied from thecompressor and combusts the mixture of the fuel and the compressed airto generate high-temperature and high-pressure combustion gas.

The turbine includes a plurality of turbine vanes and a plurality ofturbine blades which are alternately arranged in a turbine housing. Inaddition, a rotor is arranged to pass through centers of the compressor,the combustor, the turbine, and an exhaust chamber.

The rotor is rotatably supported at both ends thereof by bearings. Aplurality of disks are fixed to the rotor, and a plurality of blades areconnected to each of the disks while a drive shaft of a generator isconnected to an end of the exhaust chamber.

In a gas turbine, many system requirements should be met at each stageof the gas turbine to meet design goals. The design goals may includeoverall improved efficiency and airfoil loading capability. For example,a turbine nozzle airfoil profile should achieve thermal and mechanicaloperating requirements for that particular stage. There is thus a desirefor an improved turbine nozzle airfoil profile for use in a turbine andthe like.

SUMMARY

Aspects of one or more exemplary embodiments provide a unique airfoilprofile for a second-stage turbine nozzle capable of enhancingaeromechanics and reducing thermal and mechanical stresses.

Additional aspects will be set forth in part in the description whichfollows and, in part, will become apparent from the description, or maybe learned by practice of the exemplary embodiments.

According to an aspect of an exemplary embodiment, there is provided aturbine nozzle including: an airfoil portion having an uncoated nominalprofile substantially in accordance with Cartesian coordinate values ofX, Y, and Z set forth in Table 1. Here, the X, Y, and Z coordinates aredistances in inches measured in a Cartesian coordinate system, thecorresponding X and Y coordinates, when connected by a smooth continuousarc, define one of a plurality of airfoil profile sections at each Zdistance, and the plurality of airfoil profile sections, when joinedtogether by smooth continuous arcs, define an airfoil shape.

The airfoil shape may lie within an envelope of +/−0.120 inches measuredin a direction normal to any of the plurality of airfoil profilesections.

The X and Y coordinate values are scalable as a function of a sameconstant or number, and a set of corresponding nominal Z coordinatevalues are scalable as a function of the same constant or number toprovide at least one of a scaled up or a scaled down airfoil.

The airfoil shape may include leaned portions of airfoil to reduce asecondary flow effect.

The turbine nozzle may further include a coating applied to the airfoilshape, the coating having a thickness of less than or equal to 0.010inches.

According to an aspect of another exemplary embodiment, there isprovided a turbine including: a turbine nozzle extending from a platformto an end wall and having an airfoil-shaped cross section having aleading edge, a trailing edge, and a pressure side and a suction sideeach of which extends from the leading edge to the trailing edge,wherein the turbine nozzle may include an airfoil portion having anuncoated nominal profile substantially in accordance with Cartesiancoordinate values of X, Y, and Z set forth in Table 1. Here, the X, Y,and Z coordinates are distances in inches measured in a Cartesiancoordinate system, the corresponding X and Y coordinates, when connectedby a smooth continuous arc, define one of a plurality of airfoil profilesections at each Z distance, and the plurality of airfoil profilesections, when joined together by smooth continuous arcs, define anairfoil shape.

According to an aspect of another exemplary embodiment, there isprovided a gas turbine including: a compressor configured to compressair; a combustor configured to mix compressed air supplied from thecompressor with fuel for combustion; and a turbine including a pluralityof turbine nozzles and a plurality of turbine blades rotated bycombustion gas to generate power, wherein each of the turbine nozzlesextending from a platform to an end wall and having an airfoil-shapedcross section having a leading edge, a trailing edge, and a pressureside and a suction side each of which extends from the leading edge tothe trailing edge, and wherein the turbine nozzle may include an airfoilportion having an uncoated nominal profile substantially in accordancewith Cartesian coordinate values of X, Y, and Z set forth in Table 1.Here, the X, Y, and Z coordinates are distances in inches measured in aCartesian coordinate system, the corresponding X and Y coordinates, whenconnected by a smooth continuous arc, define one of a plurality ofairfoil profile sections at each Z distance, and the plurality ofairfoil profile sections, when joined together by smooth continuousarcs, define an airfoil shape.

BRIEF DESCRIPTION OF THE DRAWINGS

The above and other aspects will become more apparent from the followingdescription of the exemplary embodiments with reference to theaccompanying drawings, in which:

FIG. 1 is a partially cutaway perspective view illustrating a gasturbine according to an exemplary embodiment;

FIG. 2 is a cross-sectional view illustrating a schematic structure ofthe gas turbine according to the exemplary embodiment;

FIG. 3 is a schematic diagram of a turbine according to an exemplaryembodiment;

FIG. 4 is a perspective view of a second stage turbine nozzle includingan airfoil according to an exemplary embodiment;

FIG. 5 is a front view of the second stage turbine nozzle including anairfoil illustrated in FIG. 4;

FIG. 6 is a back view of the second stage turbine nozzle including anairfoil illustrated in FIG. 4; and

FIG. 7 is an airfoil shape including leaned portions of airfoilaccording to an exemplary embodiment.

DETAILED DESCRIPTION

Various modifications and various embodiments will be described below indetail with reference to the accompanying drawings so that those skilledin the art can easily carry out the disclosure. It should be understood,however, that the various embodiments are not for limiting the scope ofthe disclosure to the specific embodiment, but they should beinterpreted to include all modifications, equivalents, and alternativesof the embodiments included within the spirit and scope disclosedherein.

Hereinafter, exemplary embodiments will be described in detail withreference to the accompanying drawings. Throughout the disclosure, likereference numerals refer to like parts throughout the various figuresand exemplary embodiments. In certain embodiments, a detaileddescription of functions and configurations well known in the art may beomitted to avoid obscuring appreciation of the disclosure by a person ofordinary skill in the art. For the same reason, some components may beexaggerated, omitted, or schematically illustrated in the accompanyingdrawings.

FIG. 1 is a partially cutaway perspective view illustrating a gasturbine according to an exemplary embodiment. FIG. 2 is across-sectional view illustrating a schematic structure of the gasturbine according to the exemplary embodiment.

Referring to FIGS. 1 and 2, the gas turbine 1000 may include acompressor 1100, a combustor 1200, and a turbine 1300. Based on a flowdirection of gas (e.g., compressed air or combustion gas), thecompressor 1100 is disposed at an upstream side of the gas turbine 1000,and the turbine 1300 is disposed at a downstream side of the gas turbine1000. The combustor 1200 is disposed between the compressor 1100 and theturbine 1300.

The compressor 1100 includes compressor vanes 1120 and compressor rotorsin a compressor housing. The turbine 1300 includes turbine vane 1320 andturbine rotors in a turbine housing. The compressor vanes 1120 and thecompressor rotors are arranged in a multi-stage arrangement along theflow direction of compressed air. The turbine vanes 1320 and the turbinerotors are arranged in a multi-stage arrangement along the flowdirection of combustion gas. The compressor 1100 is designed such thatan internal space is gradually decreased in size from a front stage to arear stage so that air drawn into the compressor 1100 can be compressed.On the contrary, the turbine 1300 is designed such that an internalspace is gradually increased in size from a front stage to a rear stageso that combustion gas received from the combustor 1200 can expand.

A torque tube for transmitting a rotational torque generated by theturbine 1300 to the compressor 1100 is disposed between a compressorrotor that is located at the rearmost stage of the compressor 1100 and aturbine rotor that is located at the foremost stage of the turbine 1300.FIG. 2 illustrates a case in which the torque tube includes multipletorque tube disks arranged in a three-stage arrangement, but it isunderstood that this is only an example and other exemplary embodimentsare not limited thereto. For example, the torque tube may includemultiple torque tube disks arranged in an arrangement of equal to orgreater than four stages or an arrangement of equal to or less than twostages.

Each of the compressor rotors includes a compressor rotor disk and acompressor blade 1110 fastened to the compressor disk. That is, thecompressor 1100 includes a plurality of compressor rotor disks, andrespective compressor rotor disks are coupled to each other by a tie rodto prevent axial separation in an axial direction. The compressor rotordisks are arranged in the axial direction with the tie rod extendingthrough centers of the compressor disks. Adjacent compressor rotor disksare arranged such that opposing surfaces thereof are in tight contactwith each other by being tightly fastened by the tie rod so that theadjacent compressor rotor disks cannot rotate relative to each other.Each of the compressor rotor disks has a plurality of compressor blades1110 radially coupled to an outer circumferential surface thereof.

The compressor blades 1110 (or referred to as buckets) are radiallycoupled to an outer circumferential surface of each of the compressorrotor disks in a row. The compressor vanes 1120 (or referred to asnozzles) are provided on an inner circumferential surface of thecompressor housing in an annular row in each stage, and rows of thecompressor vanes 1120 are arranged between rows of the compressor blades1110. While the compressor disks rotate along with a rotation of the tierod, the compressor vanes 1120 fixed to the housing do not rotate. Thecompressor vanes 1120 guide the flow of compressed air moved fromfront-stage compressor blades to rear-stage compressor blades.

The tie rod is disposed to pass through centers of the plurality ofcompressor rotor disks and turbine rotor disks. One end of the tie rodis fastened to a compressor disk located at the foremost stage of thecompressor 1100, and the other end thereof is fastened in the torquetube by a fastening nut.

It is understood that the tie rod is not limited to the exampleillustrated in FIG. 2, and may be changed or vary according to one ormore other exemplary embodiments. For example, a single tie rod may bedisposed to pass through the centers of the rotor disks, a plurality oftie rods may be arranged circumferentially, or a combination thereof maybe used.

Further, a deswirler serving as a guide vane may be provided in thecompressor 1100 to adjust an actual inflow angle of the fluid enteringinto an inlet of the combustor 1200 to a designed inflow angle.

The combustor 1200 mixes the introduced compressed air with fuel, burnsa fuel-air mixture to produce high-temperature and high-pressurecombustion gas with high energy, and increases the temperature of thecombustion gas to a temperature at which the combustor and the turbinecomponents are able to withstand an isobaric combustion process.

A plurality of combustors constituting the combustor 1200 of the gasturbine may be arranged in the housing in a form of a cell. Thecombustor 1200 may include a plurality of chambers 1210 and fuel nozzlemodules 1220 arranged annually.

The high-temperature and high-pressure combustion gas supplied from thecombustor 1200 flows into the turbine 1300 and expands while passingthrough the inside of the turbine 1300, thereby applying an impulsiveforce or reaction force to the turbine blades 1310 to generate arotational torque. A portion of the rotational torque is transmitted tothe compressor via the torque tube, and a remaining portion which is anexcessive torque is used to drive a generator to produce power.

The turbine 1300 basically has a structure similar to the compressor1100. That is, the turbine 1300 may include a plurality of turbinerotors similar to the compressor rotors, and each of the turbine rotormay include a turbine rotor disk and a turbine blade 1310 fastened tothe turbine rotor disk. A plurality of turbine blades 1310 (or referredto as buckets) are radially disposed. A plurality of turbine vanes 1320(or referred to as nozzles) are fixedly arranged on an innercircumferential surface of the turbine housing in an annular row in eachstage, and rows of the turbine vanes 1320 are arranged between rows ofthe turbine blades 1310. The turbine vanes 1320 guide the flow directionof combustion gas passing through the turbine blades 1310.

FIG. 3 is a schematic diagram of the turbine 1300 according to anexemplary embodiment. FIG. 4 is a perspective view of a second stageturbine nozzle including an airfoil according to an exemplaryembodiment. FIG. 5 is a front view of the second stage turbine nozzleincluding an airfoil illustrated in FIG. 4. FIG. 6 is a back view of thesecond stage turbine nozzle including an airfoil illustrated in FIG. 4.

Referring to FIG. 3, the turbine 1300 may include a plurality of turbinestages employing a plurality of nozzles and a plurality of buckets. Forexample, a first stage comprises a plurality of circumferentially spacednozzles 20 and buckets 10. The nozzles are circumferentially spaced onefrom the other and fixed about the axis of the rotor. The first stagebuckets 10 are mounted on the turbine rotor 17. A second stage of theturbine 1300 includes a plurality of circumferentially spaced nozzles 26and buckets 16 mounted on the rotor 17. A third stage of the turbine1300 includes a plurality of circumferentially spaced nozzles 32 andbuckets 22 mounted on rotor 17. Although three stages are illustrated inFIG. 3, it is to be understood that any number of stages may be used.

Referring to FIGS. 4 to 6, the turbine nozzle 1320 according to theexemplary embodiment includes a plurality of airfoils 1330 positionedcircumferentially around the flow path of the gas turbine 1000. Eachairfoil 1330 extends between a leading edge 1332 and a trailing edge1331 in a stream wise direction and between a platform 1340 and an endwall 1342 in a spanwise direction. Each airfoil 1330 is attached to theend wall 1342 of the airfoil 1330. The airfoils 1330 can be integrallyformed with the end wall 1342 through a casting process or the like oralternatively may be mechanically joined via welding or brazing.

Each airfoil 1330 includes a pressure side 1333 and a suction side 1334.The pressure side 1333 and the suction side 1334 which are formed toextend from the leading edge 1332 to the trailing edge 1331 provideaerodynamic control of the flow of working fluid so as to optimizeefficiency in the turbine 1300. That is, the turbine vane airfoil 1330extending from the platform 1340 to the end wall 1342 has anairfoil-shaped cross section having the leading edge 1332, the trailingedge 1331, the pressure side 1333, and the suction side 1334.

The airfoil shape may be defined by a loci of points in space that meetstage design requirements. These points are unique and specific to thesystem. The list of X, Y, and Z coordinates for the airfoil, which areincluded as Table 1, has been optimized for stage efficiency,aerodynamic efficiency, and thermal and mechanical life requirements. Inone exemplary embodiment, the points may be arrived at by iterationbetween aerodynamic and mechanical design optimization. Accordingly,these are the only loci of points that allow the gas turbine to run atthe most efficient, safe and smooth manner.

Referring to FIGS. 4 to 6, the airfoil shape of the exemplary embodimentis defined by a unique set or loci of points in space that may bedelineated. As shown in Table 1, the loci that defines the shape of theairfoil may include a set of approximately 1,440 points with X, Y and Zcoordinates. The X, Y and Z coordinates, which represent the airfoilshape, are created in a coordinate system which is defined relative tothe cold rotor centerline axis of the gas turbine (i.e., X coordinateaxis). The origin of the coordinate system on the cold rotor centerlineaxis is defined as X=0.0, Y=0.0 and Z=0.0. For example, the coordinatesystem is set relative to the airfoil and is fully defined by points A,B and C. Points A and B are both located 40.900 inches above the coldrotor centerline axis. Point A lies at an intersection of the airfoilmean camber line and the leading-edge airfoil surface. Point B lies atan intersection of the airfoil mean camber line and the trailing-edgeairfoil surface. Point C is located 47.200 inches above the cold rotorcenterline axis and lies at the intersection of the airfoil mean camberline and the airfoil trailing-edge surface. Here, a coordinate systemorigin is located at point A. Points A and B define the positive X-axis.Points A, B and C define the positive X-Z plane. The Y-axis is thendefined using the right-hand rule methodology. The coordinate values forthe X, Y and Z coordinates are set forth in inches in Table 1, althoughother units of dimensions may be used if the values are appropriatelyconverted.

The Cartesian coordinate system of X, Y and Z values given in Table 1below defines the shape of the airfoil according to an exemplaryembodiment. More specifically, the shape of the airfoil is defined bythe cloud of points listed such that airfoil could be constructed bydefining approximately smooth sheet surfaces through the listed points.As one of ordinary skill in the art will appreciate, Table 1 values aregenerated and shown to three decimal places for determining the profileof airfoil. All of the 1440 points represent a nominal cold or roomtemperature shape of the airfoil. It will be appreciated that as thenozzle heats up in operation, mechanical loading and temperature willcause a change in X, Y and Z coordinates. Accordingly, values for theairfoil shape given in Table 1 represent ambient, non-operating ornon-hot conditions.

The coordinate values set forth in Table 1 below are for a coldcondition of the turbine nozzle (e.g., non-rotating state and at roomtemperature). Further, the coordinate values set forth in Table 1 arefor an uncoated nominal three-dimensional (3D) shape of the turbinenozzle. In some aspects, a coating (e.g., corrosion protective coating)may be applied to the turbine nozzle. The coating thickness may up toabout 0.010 inches thick.

Further, the turbine nozzle 1320 may be fabricated using a variety ofmanufacturing techniques, such as forging, casting, milling,electro-chemical machining, electric-discharge machining, and the like.As such, the turbine nozzle may have a series of manufacturingtolerances for the position, profile, twist, and chord that can causethe turbine nozzle to vary from the nominal 3D shape defined by thecoordinate values set forth in Table 1. This manufacturing tolerance maybe, for example, +/−0.120 inches in a direction away from any of thecoordinate values of Table 1 without departing from the scope of thesubject matter described herein.

In addition to manufacturing tolerances affecting the overall size ofthe turbine nozzle, it is also possible to scale the airfoil to a largeror smaller airfoil size. In order to maintain the benefits of this 3Dshape, in terms of stiffness and stress, it is necessary to scale theturbine nozzle uniformly in the X, Y, and Z directions.

The Table 1 values are generated and shown for determining the profileof the airfoil. There are typical manufacturing tolerances as well ascoatings which must be accounted for in the actual profile of theairfoil. Each section is joined smoothly with the other sections to formthe complete airfoil shape. It will therefore be appreciated that+/−typical manufacturing tolerances, i.e., +/−values, including anycoating thicknesses, are additive to the X, Y and Z values given inTable 1 below.

TABLE 1 X Y Z Section 1 Point 1 7.608 −0.088 −1.422 Point 2 7.532 −0.206−1.437 Point 3 7.608 −0.088 −1.422 Point 4 7.468 −0.104 −1.424 Point 57.328 −0.181 −1.434 Point 6 7.187 −0.257 −1.443 Point 7 7.045 −0.332−1.453 Point 8 6.903 −0.404 −1.462 Point 9 6.760 −0.476 −1.471 Point 106.616 −0.546 −1.479 Point 11 6.471 −0.614 −1.488 Point 12 6.325 −0.680−1.496 Point 13 6.179 −0.745 −1.504 Point 14 6.032 −0.808 −1.512 Point15 5.884 −0.869 −1.520 Point 16 5.735 −0.928 −1.527 Point 17 5.585−0.984 −1.534 Point 18 5.435 −1.039 −1.541 Point 19 5.283 −1.091 −1.548Point 20 5.131 −1.140 −1.554 Point 21 4.978 −1.187 −1.560 Point 22 4.824−1.231 −1.565 Point 23 4.669 −1.273 −1.571 Point 24 4.514 −1.311 −1.575Point 25 4.358 −1.346 −1.580 Point 26 4.201 −1.378 −1.584 Point 27 4.043−1.406 −1.587 Point 28 3.885 −1.431 −1.590 Point 29 3.726 −1.452 −1.593Point 30 3.567 −1.468 −1.595 Point 31 3.407 −1.480 −1.597 Point 32 3.247−1.487 −1.597 Point 33 3.087 −1.489 −1.598 Point 34 2.926 −1.485 −1.597Point 35 2.767 −1.474 −1.596 Point 36 2.607 −1.457 −1.594 Point 37 2.449−1.433 −1.591 Point 38 2.292 −1.400 −1.587 Point 39 2.138 −1.359 −1.581Point 40 1.986 −1.308 −1.575 Point 41 1.838 −1.247 −1.567 Point 42 1.695−1.175 −1.558 Point 43 1.558 −1.093 −1.548 Point 44 1.428 −1.000 −1.536Point 45 1.305 −0.898 −1.524 Point 46 1.191 −0.787 −1.510 Point 47 1.083−0.669 −1.495 Point 48 0.980 −0.547 −1.480 Point 49 0.880 −0.423 −1.464Point 50 0.778 −0.300 −1.449 Point 51 0.666 −0.187 −1.434 Point 52 0.535−0.096 −1.423 Point 53 0.382 −0.052 −1.417 Point 54 0.223 −0.063 −1.419Point 55 0.090 −0.145 −1.429 Point 56 0.000 −0.276 −1.446 Point 57−0.069 −0.419 −1.464 Point 58 −0.123 −0.569 −1.482 Point 59 −0.163−0.723 −1.502 Point 60 −0.191 −0.879 −1.521 Point 61 −0.206 −1.037−1.541 Point 62 −0.209 −1.196 −1.561 Point 63 −0.200 −1.355 −1.581 Point64 −0.178 −1.512 −1.601 Point 65 −0.145 −1.668 −1.620 Point 66 −0.100−1.820 −1.639 Point 67 −0.043 −1.969 −1.658 Point 68 0.024 −2.113 −1.676Point 69 0.103 −2.252 −1.693 Point 70 0.192 −2.384 −1.710 Point 71 0.292−2.508 −1.726 Point 72 0.402 −2.624 −1.740 Point 73 0.522 −2.729 −1.753Point 74 0.651 −2.823 −1.765 Point 75 0.789 −2.903 −1.775 Point 76 0.934−2.971 −1.784 Point 77 1.085 −3.024 −1.790 Point 78 1.240 −3.063 −1.795Point 79 1.398 −3.089 −1.798 Point 80 1.558 −3.102 −1.800 Point 81 1.718−3.103 −1.800 Point 82 1.878 −3.094 −1.799 Point 83 2.037 −3.075 −1.797Point 84 2.195 −3.049 −1.793 Point 85 2.352 −3.015 −1.789 Point 86 2.507−2.975 −1.784 Point 87 2.660 −2.930 −1.778 Point 88 2.812 −2.879 −1.772Point 89 2.963 −2.825 −1.765 Point 90 3.112 −2.768 −1.758 Point 91 3.260−2.707 −1.750 Point 92 3.407 −2.643 −1.742 Point 93 3.553 −2.577 −1.734Point 94 3.698 −2.509 −1.726 Point 95 3.842 −2.439 −1.717 Point 96 3.985−2.368 −1.708 Point 97 4.127 −2.294 −1.699 Point 98 4.268 −2.220 −1.689Point 99 4.409 −2.144 −1.680 Point 100 4.550 −2.068 −1.670 Point 1014.689 −1.990 −1.661 Point 102 4.829 −1.911 −1.651 Point 103 4.967 −1.832−1.641 Point 104 5.106 −1.751 −1.631 Point 105 5.243 −1.670 −1.620 Point106 5.381 −1.588 −1.610 Point 107 5.518 −1.506 −1.600 Point 108 5.654−1.423 −1.589 Point 109 5.791 −1.340 −1.579 Point 110 5.927 −1.255−1.568 Point 111 6.062 −1.171 −1.558 Point 112 6.198 −1.086 −1.547 Point113 6.333 −1.000 −1.536 Point 114 6.467 −0.914 −1.526 Point 115 6.602−0.827 −1.515 Point 116 6.736 −0.740 −1.504 Point 117 6.869 −0.652−1.493 Point 118 7.003 −0.564 −1.482 Point 119 7.136 −0.475 −1.471 Point120 7.268 −0.386 −1.459 Section 2 Point 1 7.777 −0.025 −0.406 Point 27.632 −0.040 −0.408 Point 3 7.486 −0.118 −0.418 Point 4 7.339 −0.195−0.428 Point 5 7.192 −0.271 −0.437 Point 6 7.044 −0.344 −0.446 Point 76.895 −0.417 −0.455 Point 8 6.745 −0.488 −0.464 Point 9 6.594 −0.557−0.473 Point 10 6.443 −0.624 −0.481 Point 11 6.290 −0.689 −0.490 Point12 6.137 −0.752 −0.498 Point 13 5.983 −0.814 −0.505 Point 14 5.829−0.873 −0.513 Point 15 5.673 −0.930 −0.520 Point 16 5.516 −0.985 −0.527Point 17 5.359 −1.037 −0.533 Point 18 5.201 −1.087 −0.539 Point 19 5.042−1.135 −0.545 Point 20 4.882 −1.179 −0.551 Point 21 4.722 −1.221 −0.556Point 22 4.561 −1.259 −0.561 Point 23 4.399 −1.295 −0.566 Point 24 4.236−1.327 −0.570 Point 25 4.072 −1.355 −0.573 Point 26 3.908 −1.380 −0.576Point 27 3.744 −1.401 −0.579 Point 28 3.579 −1.418 −0.581 Point 29 3.413−1.430 −0.582 Point 30 3.247 −1.437 −0.583 Point 31 3.082 −1.438 −0.584Point 32 2.916 −1.434 −0.583 Point 33 2.750 −1.424 −0.582 Point 34 2.585−1.406 −0.580 Point 35 2.421 −1.382 −0.576 Point 36 2.258 −1.349 −0.572Point 37 2.098 −1.308 −0.567 Point 38 1.940 −1.257 −0.561 Point 39 1.786−1.197 −0.553 Point 40 1.636 −1.126 −0.544 Point 41 1.492 −1.045 −0.534Point 42 1.353 −0.954 −0.523 Point 43 1.222 −0.854 −0.510 Point 44 1.097−0.745 −0.497 Point 45 0.978 −0.631 −0.482 Point 46 0.863 −0.512 −0.467Point 47 0.749 −0.392 −0.452 Point 48 0.635 −0.273 −0.437 Point 49 0.512−0.162 −0.423 Point 50 0.376 −0.068 −0.412 Point 51 0.221 −0.012 −0.405Point 52 0.056 −0.014 −0.405 Point 53 −0.090 −0.088 −0.414 Point 54−0.191 −0.217 −0.430 Point 55 −0.265 −0.364 −0.449 Point 56 −0.321−0.519 −0.468 Point 57 −0.360 −0.679 −0.488 Point 58 −0.384 −0.842−0.509 Point 59 −0.395 −1.006 −0.529 Point 60 −0.393 −1.171 −0.550 Point61 −0.377 −1.335 −0.571 Point 62 −0.350 −1.497 −0.591 Point 63 −0.311−1.657 −0.611 Point 64 −0.260 −1.814 −0.631 Point 65 −0.197 −1.966−0.650 Point 66 −0.123 −2.113 −0.668 Point 67 −0.038 −2.255 −0.686 Point68 0.058 −2.389 −0.703 Point 69 0.166 −2.514 −0.718 Point 70 0.283−2.630 −0.733 Point 71 0.411 −2.735 −0.746 Point 72 0.548 −2.828 −0.758Point 73 0.693 −2.908 −0.768 Point 74 0.845 −2.973 −0.776 Point 75 1.003−3.025 −0.783 Point 76 1.164 −3.063 −0.787 Point 77 1.328 −3.088 −0.790Point 78 1.493 −3.101 −0.792 Point 79 1.659 −3.102 −0.792 Point 80 1.825−3.093 −0.791 Point 81 1.990 −3.076 −0.789 Point 82 2.154 −3.050 −0.786Point 83 2.316 −3.017 −0.782 Point 84 2.478 −2.978 −0.777 Point 85 2.637−2.934 −0.771 Point 86 2.796 −2.885 −0.765 Point 87 2.953 −2.831 −0.758Point 88 3.108 −2.774 −0.751 Point 89 3.263 −2.714 −0.744 Point 90 3.416−2.651 −0.736 Point 91 3.568 −2.585 −0.727 Point 92 3.719 −2.516 −0.719Point 93 3.869 −2.446 −0.710 Point 94 4.018 −2.374 −0.701 Point 95 4.166−2.300 −0.692 Point 96 4.313 −2.224 −0.682 Point 97 4.460 −2.147 −0.672Point 98 4.606 −2.069 −0.663 Point 99 4.751 −1.989 −0.653 Point 1004.896 −1.909 −0.643 Point 101 5.040 −1.827 −0.632 Point 102 5.184 −1.745−0.622 Point 103 5.327 −1.661 −0.611 Point 104 5.469 −1.577 −0.601 Point105 5.611 −1.492 −0.590 Point 106 5.753 −1.406 −0.580 Point 107 5.894−1.320 −0.569 Point 108 6.035 −1.233 −0.558 Point 109 6.176 −1.145−0.547 Point 110 6.316 −1.057 −0.536 Point 111 6.456 −0.968 −0.525 Point112 6.595 −0.879 −0.513 Point 113 6.734 −0.789 −0.502 Point 114 6.873−0.699 −0.491 Point 115 7.011 −0.608 −0.479 Point 116 7.149 −0.517−0.468 Point 117 7.287 −0.425 −0.456 Point 118 7.424 −0.333 −0.445 Point119 7.561 −0.240 −0.433 Point 120 7.698 −0.147 −0.422 Section 3 Point 17.940 0.028 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Point 740.480 −2.830 0.250 Point 75 0.632 −2.908 0.240 Point 76 0.790 −2.9710.232 Point 77 0.953 −3.022 0.226 Point 78 1.119 −3.059 0.221 Point 791.288 −3.083 0.218 Point 80 1.458 −3.096 0.216 Point 81 1.629 −3.0990.216 Point 82 1.800 −3.092 0.217 Point 83 1.970 −3.076 0.219 Point 842.139 −3.052 0.222 Point 85 2.307 −3.021 0.226 Point 86 2.473 −2.9840.230 Point 87 2.639 −2.941 0.236 Point 88 2.802 −2.894 0.242 Point 892.965 −2.841 0.248 Point 90 3.126 −2.785 0.255 Point 91 3.286 −2.7250.263 Point 92 3.444 −2.662 0.271 Point 93 3.601 −2.596 0.279 Point 943.757 −2.527 0.288 Point 95 3.912 −2.456 0.297 Point 96 4.066 −2.3820.306 Point 97 4.219 −2.307 0.315 Point 98 4.371 −2.229 0.325 Point 994.522 −2.150 0.335 Point 100 4.672 −2.070 0.345 Point 101 4.821 −1.9880.355 Point 102 4.970 −1.904 0.366 Point 103 5.118 −1.820 0.376 Point104 5.265 −1.734 0.387 Point 105 5.412 −1.648 0.398 Point 106 5.559−1.560 0.409 Point 107 5.704 −1.472 0.420 Point 108 5.850 −1.383 0.431Point 109 5.995 −1.294 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Point 36 2.472 −1.303 3.465 Point 372.292 −1.273 3.469 Point 38 2.112 −1.236 3.473 Point 39 1.935 −1.1933.479 Point 40 1.759 −1.142 3.485 Point 41 1.586 −1.083 3.492 Point 421.415 −1.018 3.500 Point 43 1.247 −0.947 3.509 Point 44 1.082 −0.8683.519 Point 45 0.920 −0.784 3.530 Point 46 0.761 −0.695 3.541 Point 470.604 −0.602 3.553 Point 48 0.449 −0.505 3.565 Point 49 0.295 −0.4083.577 Point 50 0.140 −0.312 3.589 Point 51 −0.018 −0.220 3.601 Point 52−0.181 −0.137 3.611 Point 53 −0.352 −0.073 3.619 Point 54 −0.532 −0.0423.623 Point 55 −0.713 −0.063 3.620 Point 56 −0.875 −0.144 3.610 Point 57−0.980 −0.291 3.592 Point 58 −1.044 −0.461 3.570 Point 59 −1.078 −0.6393.548 Point 60 −1.089 −0.820 3.525 Point 61 −1.081 −1.001 3.503 Point 62−1.056 −1.181 3.480 Point 63 −1.015 −1.358 3.458 Point 64 −0.960 −1.5313.436 Point 65 −0.892 −1.699 3.415 Point 66 −0.811 −1.862 3.395 Point 67−0.719 −2.019 3.375 Point 68 −0.615 −2.168 3.356 Point 69 −0.501 −2.3103.339 Point 70 −0.376 −2.443 3.322 Point 71 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Point 64 −2.142 −1.861 9.442 Point 65 −2.000 −2.028 9.421 Point 66−1.848 −2.185 9.401 Point 67 −1.688 −2.334 9.383 Point 68 −1.519 −2.4749.365 Point 69 −1.343 −2.605 9.349 Point 70 −1.161 −2.727 9.333 Point 71−0.973 −2.840 9.319 Point 72 −0.780 −2.944 9.306 Point 73 −0.582 −3.0399.294 Point 74 −0.380 −3.124 9.283 Point 75 −0.174 −3.200 9.274 Point 760.036 −3.266 9.266 Point 77 0.248 −3.322 9.259 Point 78 0.463 −3.3689.253 Point 79 0.679 −3.404 9.248 Point 80 0.898 −3.431 9.245 Point 811.117 −3.447 9.243 Point 82 1.337 −3.453 9.242 Point 83 1.556 −3.4509.242 Point 84 1.776 −3.438 9.244 Point 85 1.994 −3.417 9.247 Point 862.212 −3.388 9.250 Point 87 2.429 −3.350 9.255 Point 88 2.644 −3.3059.261 Point 89 2.857 −3.253 9.267 Point 90 3.069 −3.194 9.275 Point 913.279 −3.129 9.283 Point 92 3.487 −3.058 9.292 Point 93 3.693 −2.9839.301 Point 94 3.897 −2.902 9.311 Point 95 4.099 −2.817 9.322 Point 964.300 −2.728 9.333 Point 97 4.499 −2.636 9.345 Point 98 4.697 −2.5409.357 Point 99 4.893 −2.442 9.369 Point 100 5.087 −2.341 9.382 Point 1015.281 −2.237 9.395 Point 102 5.473 −2.131 9.408 Point 103 5.664 −2.0239.421 Point 104 5.854 −1.914 9.435 Point 105 6.043 −1.803 9.449 Point106 6.232 −1.691 9.463 Point 107 6.420 −1.577 9.477 Point 108 6.607−1.463 9.492 Point 109 6.793 −1.348 9.506 Point 110 6.979 −1.231 9.521Point 111 7.165 −1.115 9.535 Point 112 7.350 −0.997 9.550 Point 1137.535 −0.879 9.565 Point 114 7.720 −0.761 9.580 Point 115 7.904 −0.6429.595 Point 116 8.088 −0.523 9.610 Point 117 8.272 −0.404 9.624 Point118 8.456 −0.285 9.639 Point 119 8.640 −0.166 9.654 Point 120 8.824−0.046 9.669

FIG. 7 illustrates an airfoil shape including leaned portions 1360 ofairfoil according to an exemplary embodiment. As the turbine nozzlescome into direct contact with the high-temperature and high-pressurecombustion gas, a secondary flow occurs. For example, secondary flowsare flow effects that occur after the high-temperature and high-pressurecombustion gas path flow contacts the turbine nozzles. The flow effectsare not good as they negatively affect aerodynamic performance, causingturbulence in the flow path. Further, the turbulences may increase theheat transfer coefficients on the gas path surface which also increasesheat transfer/metal temperature rise by increasing the heat transfercoefficient of the gas path surface. In order to reduce losses caused bythe secondary flows, a newly designed airfoil shape is needed. Accordingto the newly designed airfoil shape of the exemplary embodiment whichincludes leaned portions 1360 of airfoil as illustrated in FIG. 7, it ispossible to reduce the secondary flow effects aerodynamically bychanging the shape/contour of the airfoil.

While one or more exemplary embodiments have been described withreference to the accompanying drawings, it is to be understood by thoseskilled in the art that various modifications and changes in form anddetails can be made therein without departing from the spirit and scopeas defined by the appended claims. Therefore, the description of theexemplary embodiments should be construed in a descriptive sense onlyand not to limit the scope of the claims, and many alternatives,modifications, and variations will be apparent to those skilled in theart.

What is claimed is:
 1. A turbine nozzle comprising: an airfoil portionhaving an uncoated nominal profile substantially in accordance withCartesian coordinate values of X, Y, and Z set forth in Table 1, whereinthe X, Y, and Z coordinates are distances in inches measured in aCartesian coordinate system, wherein, at each Z distance, thecorresponding X and Y coordinates, when connected by a smooth continuousarc, define one of a plurality of airfoil profile sections, and whereinthe plurality of airfoil profile sections, when joined together bysmooth continuous arcs, define an airfoil shape.
 2. The turbine nozzleaccording to claim 1, wherein the airfoil shape lies within an envelopeof +/−0.120 inches measured in a direction normal to any of theplurality of airfoil profile sections.
 3. The turbine nozzle accordingto claim 1, wherein the X and Y coordinate values are scalable as afunction of a same constant or number and a set of corresponding nominalZ coordinate values are scalable as a function of the same constant ornumber to provide at least one of a scaled up or a scaled down airfoil.4. The turbine nozzle according to claim 3, wherein the airfoil shapeincludes leaned portions of airfoil to reduce a secondary flow effect.5. The turbine nozzle according to claim 1, further comprising a coatingapplied to the airfoil shape, the coating having a thickness of lessthan or equal to 0.010 inches.
 6. A turbine comprising: a turbine nozzleextending from a platform to an end wall and having an airfoil-shapedcross section having a leading edge, a trailing edge, and a pressureside and a suction side each of which extends from the leading edge tothe trailing edge, wherein the turbine nozzle comprises an airfoilportion having an uncoated nominal profile substantially in accordancewith Cartesian coordinate values of X, Y, and Z set forth in Table 1,wherein the X, Y, and Z coordinates are distances in inches measured ina Cartesian coordinate system, wherein, at each Z distance, thecorresponding X and Y coordinates, when connected by a smooth continuousarc, define one of a plurality of airfoil profile sections, and whereinthe plurality of airfoil profile sections, when joined together bysmooth continuous arcs, define an airfoil shape.
 7. The turbineaccording to claim 6, wherein the airfoil shape lies within an envelopeof +/−0.120 inches measured in a direction normal to any of theplurality of airfoil profile sections.
 8. The turbine according to claim6, wherein the X and Y coordinate values are scalable as a function of asame constant or number and a set of corresponding nominal Z coordinatevalues are scalable as a function of the same constant or number toprovide at least one of a scaled up or a scaled down airfoil.
 9. Theturbine according to claim 8, wherein the airfoil shape includes leanedportions of airfoil to reduce a secondary flow effect.
 10. The turbineaccording to claim 6, further comprising a coating applied to theairfoil shape, the coating having a thickness of less than or equal to0.010 inches.
 11. A gas turbine comprising: a compressor configured tocompress air; a combustor configured to mix compressed air supplied fromthe compressor with fuel for combustion to generate combustion gas; anda turbine comprising a plurality of turbine nozzles and a plurality ofturbine blades rotated by the combustion gas to generate power, whereineach of the turbine nozzles extending from a platform to an end wall andhaving an airfoil-shaped cross section having a leading edge, a trailingedge, and a pressure side and a suction side each of which extends fromthe leading edge to the trailing edge, wherein the turbine nozzlecomprises an airfoil portion having an uncoated nominal profilesubstantially in accordance with Cartesian coordinate values of X, Y,and Z set forth in Table 1, wherein the X, Y, and Z coordinates aredistances in inches measured in a Cartesian coordinate system, wherein,at each Z distance, the corresponding X and Y coordinates, whenconnected by a smooth continuous arc, define one of a plurality ofairfoil profile sections, and wherein the plurality of airfoil profilesections, when joined together by smooth continuous arcs, define anairfoil shape.
 12. The gas turbine according to claim 11, wherein theairfoil shape lies within an envelope of +/−0.120 inches measured in adirection normal to any of the plurality of airfoil profile sections.13. The turbine according to claim 11, wherein the X and Y coordinatevalues are scalable as a function of a same constant or number and a setof corresponding nominal Z coordinate values are scalable as a functionof the same constant or number to provide at least one of a scaled up ora scaled down airfoil.
 14. The gas turbine according to claim 13,wherein the airfoil shape includes leaned portions of airfoil to reducea secondary flow effect.
 15. The gas turbine according to claim 11,further comprising a coating applied to the airfoil shape, the coatinghaving a thickness of less than or equal to 0.010 inches.